EP1298230A1 - Procédé pour enlever des produits de corrosion d'un composant métallique - Google Patents

Procédé pour enlever des produits de corrosion d'un composant métallique Download PDF

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Publication number
EP1298230A1
EP1298230A1 EP01123593A EP01123593A EP1298230A1 EP 1298230 A1 EP1298230 A1 EP 1298230A1 EP 01123593 A EP01123593 A EP 01123593A EP 01123593 A EP01123593 A EP 01123593A EP 1298230 A1 EP1298230 A1 EP 1298230A1
Authority
EP
European Patent Office
Prior art keywords
component
cleaning agent
impregnating
corrosion products
metal
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP01123593A
Other languages
German (de)
English (en)
Inventor
Norbert Dr. Czech
Andre Dr. Jeutter
Adrian Kempster
Ralph Reiche
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
Diffusion Alloys Ltd
Original Assignee
Siemens AG
Diffusion Alloys Ltd
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Siemens AG, Diffusion Alloys Ltd filed Critical Siemens AG
Priority to EP01123593A priority Critical patent/EP1298230A1/fr
Priority to US10/490,567 priority patent/US7138065B2/en
Priority to JP2003532728A priority patent/JP2005504179A/ja
Priority to PCT/EP2002/005490 priority patent/WO2003029521A1/fr
Priority to DE50202441T priority patent/DE50202441D1/de
Priority to CNB028170555A priority patent/CN1328413C/zh
Priority to EP02730264A priority patent/EP1432847B8/fr
Publication of EP1298230A1 publication Critical patent/EP1298230A1/fr
Priority to US11/541,253 priority patent/US7429337B2/en
Withdrawn legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/288—Protective coatings for blades
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C10/00—Solid state diffusion of only metal elements or silicon into metallic material surfaces
    • C23C10/28—Solid state diffusion of only metal elements or silicon into metallic material surfaces using solids, e.g. powders, pastes
    • C23C10/30—Solid state diffusion of only metal elements or silicon into metallic material surfaces using solids, e.g. powders, pastes using a layer of powder or paste on the surface
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23G—CLEANING OR DE-GREASING OF METALLIC MATERIAL BY CHEMICAL METHODS OTHER THAN ELECTROLYSIS
    • C23G5/00—Cleaning or de-greasing metallic material by other methods; Apparatus for cleaning or de-greasing metallic material with organic solvents
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/005—Repairing methods or devices
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2230/00—Manufacture
    • F05B2230/90—Coating; Surface treatment
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/90—Coating; Surface treatment

Definitions

  • the invention relates to a method for removing corrosion products an at least partially corroded component made of metal or a metal compound, in which a Multi-component detergent in a simple manner is applied to the corroded component, resulting in after a heat treatment of the component with the cleaning agent remove or remove the corrosion products more easily to let.
  • Ceramic thermal barrier coatings have been developed on thermally stressed components, for example superalloys, be applied, the alone the high inlet temperatures in the long run could not stand.
  • the Ceramic thermal barrier coating offers the advantage of a high Temperature resistance due to their ceramic properties and the metallic substrate offers the advantage of good mechanical Properties in this composite or layer system.
  • composition of these MCrAlY layers can vary, however, all MCrAlY layers are subject despite the overlying Ceramic layer of corrosion by oxidation, sulfidation, Nitridation or other chemical and / or mechanical Attacks.
  • the MCrAlY layer often degrades in a stronger one Dimensions as the metallic substrate, i. the life of the Composite system of substrate and layer is determined by the lifetime of the MCrAlY layer.
  • the McrAlY interlayer is only after prolonged use conditionally functional, however, the substrate can still be fully functional.
  • a process for the removal of corrosion products is out the US-PS 6,217,668 known.
  • the corroded component housed in a large crucible, wherein the component in a powder bed with an aluminum source is arranged.
  • the crucible must be partially completed and then be heated in an oven.
  • Aluminum is supplied to the corroded component, whereby the areas by a subsequent acid treatment can be removed, which previously could be removed worse, So had a higher resistance to erosion.
  • the powder bed requires a lot of material and the crucible takes up a lot of space in the oven during the heat treatment.
  • the heat process also takes because of the large heat capacity longer.
  • the invention overcomes the disadvantages described a method as described in claim 1.
  • the method according to the invention has the advantage that in a simple way corroded components of corrosion products be removed. It is possible for the first time the deposition of an impregnating substance from the gas phase perform in a locally controllable procedure, so that it is in spite of the gaseous compound with the impregnating substance does not come to an impregnation in areas which should remain untreated.
  • the ablation can be achieved by mechanical methods, e.g. Sandblasting, Water jets, dry ice blasting, and / or by chemical processes, e.g. an acid treatment.
  • the detergent on the component at least partially liable, can in an advantageous manner, for example. Front and Rear side of the component at the same time according to the invention Procedure of corrosion products are removed.
  • the adhesion of the cleaning agent on the component can on advantageous manner done by the fact that the detergent has a paste-like consistency, for example the cleaning agent has a binder.
  • the cleaning agent can also be used with a carrier liquid be mixed with or without binder and brushed on the component or the component is dipped in a flowable mass of liquid and detergent coated with the detergent.
  • the cleaning agent can also be beneficial be applied only locally on the component, since areas, which are not corroded, no application of the cleaning agent require cleaning agents are saved can.
  • the application of the cleaning agent is advantageously carried out near the corrosion products because it causes the at least one component of the cleaning agent has short diffusion paths during the heat treatment.
  • the cleaning agent is, for example, in a thin layer the component is applied so that in relation to the embedding of the Component consumed in a powder bed significantly less material becomes.
  • the crucible heat treatment means that in the oven less space through the voluminous crucible is consumed, allowing more components in a furnace cycle can be accommodated, which reduces the process costs.
  • the reduction of the masses of the component and the cleaning agent means that less mass needs to be heated.
  • an ablation process for example an acid treatment
  • the surface of the non-corroded component becomes uniform ablated.
  • the corrosion creates areas of the component and / or corrosion products resulting from the acid treatment not so easy to remove or remove, So they are more resistant to erosion. This leads to a Acid treatment as ablation process to an unwanted, uneven erosion.
  • the formation of at least one sacrificial zone in the erosion resistant Areas of the component causes the during the corrosion of erosion resistant areas itself how to remove material from the non-corroded component.
  • the sacrificial zone advantageously has MCrAlY layers a metallic impregnating component, advantageously Aluminum, aluminum compound or an aluminum alloy on,
  • the cleaning agent may be advantageous to the metal component Way also included in the form of a metal complex.
  • the mixing of a metallic one is omitted Powder with a carrier substance or the activating agent.
  • the impregnating component must be removed from the cleaning agent at least partially diffuse into the component. This happens advantageously in that the impregnating component is applied in gaseous form to the component.
  • the gaseous Compound is formed by a reaction with the activating agent, wherein the impregnating agent advantageously does not melt, causing the process temperatures and thus process costs are reduced.
  • halogen compounds such as ammonia, which forms aluminum with aluminum chloride.
  • the formation of the gaseous compound can be controlled by advantageously adding a carrier substance, for example aluminum oxide, to the cleaning agent, whereby the gas formation is controlled and uniform.
  • the method is advantageously suitable for layer systems, such as turbine blades, which have a layer system consisting of a metallic substrate, an MCrAlY layer and a ceramic thermal barrier coating applied thereto.
  • the cleaning agent contains aluminum as a metallic component
  • aluminum re-accumulates in the previous aluminum-depleted regions of the MCrAlY layer, so that acid treatment dissolves these areas, such as the MCrAlY layer, causing them to collect Areas containing corrosion products to be replaced with.
  • the area of detergent on the component near the surface is disposed of the component, depleted at the at least one Impregnation.
  • the heat treatment is over, if the victim zones are large enough, i. in case of MCrAlY layer sufficient on aluminum depleted areas again enriched with aluminum. If not that Case, the detergent can be removed and that Component can then be subjected to a thermal treatment, wherein advantageously the impregnating component of Detergent already in the component by diffusion is present, penetrate by diffusion deeper into the component leaves and thus the victim zone or sacrificial layer on advantageous Fashion enlarged in depth.
  • An optimal temperature of the thermal treatment is above the temperature of the heat treatment to the solution annealing temperature of the component.
  • FIG. 1a shows a component 1 made of metal, a metal alloy or of a metal compound attached to a surface 7 outer corrosion products 4 and / or inside the component 1 internal corrosion products 5, the example in Separate areas are available.
  • the corrosion products 4 may also be contiguous, or be present on the entire surface 7, so one Form corrosion layer.
  • the component 1 may be solid or a layer or a region a composite or layer system 16 (Fig. 2).
  • the corrosion products 4, 5 have become during the use of the Component 1 formed and are for further use of the Component 1 undesirable and must be removed. This happens often by a treatment in an acid bath.
  • the method according to the invention makes it possible to use the corrosion products completely and evenly with the material of the Component 1 to remove.
  • a coarse Removal of corrosion products or other areas by mechanical methods e.g. Sandblasting, and / or chemical Means, e.g. Acid bath, done.
  • the cleaning agent 10 contains at least one impregnating component 13, which in a heat treatment with at least one Activation component of the cleaning agent 10 to at least a gaseous compound reacts.
  • the gaseous compound becomes the impregnating component 13 is brought into contact with the component 1 or beats down there and forms there, for example, an impregnation layer. Out this impregnation layer or directly from the gaseous compound diffuses the impregnating agent in the areas with the corrosion products 4, 5 a. The impregnating component 13 is then at least partially in the areas with the corrosion products 4, 5 available.
  • the acid treatment reduces a thickness of the component 1, which varies from a thickness d (FIG. 1c) to a smaller one Thickness d '(FIG. 1d).
  • Fig. 1d shows a component 1 without internal and external corrosion products 4, 5 due to the treatment according to the invention Method.
  • the choice of the material of the at least one impregnating component depends on the composition of the material of the component 1 and / or the corrosion products 4, 5 from.
  • the activation component has the task of the impregnating component to bring to the surface 7 of the part. This happens because the activation component with the Impregnating component can form a gaseous compound, which can be deposited on the surface 7 of the component 1. To this end, e.g. Halogen compounds into consideration.
  • FIG. 2 a shows, as a component 1, a layer system 16 which for example, by a turbine blade or vane is formed.
  • the layer system 16 in this case consists of a substrate 19, for example a superalloy, for example the base composition Ni 3 Al.
  • a layer 22 is applied, for example of the composition MCrAlY, where M stands for a chemical element Cr, Ni or Fe.
  • This so-called MCrAlY layer forms a corrosion protection layer, which can also act as an adhesion-promoting layer for a ceramic thermal insulation layer (not shown) applied to the layer 22.
  • the layer system 16 it comes, for example. for the oxidation, nitridation or sulfidation of the MCrAlY layer 22, so in the layer 22 areas with corrosion products 4, 5 (not shown).
  • the corrosion products 4, 5 form an at least partially existing layer in or on or below a surface 7 Layer of the component 16.
  • These corrosion products 4 for example alumina or other aluminum compounds, remove the MCrAlY layer 22 Aluminum, so that in the area surrounding the area with the Corrosion products 4, mainly below, i. in the direction of the substrate 19, the corrosion products, at least one sacrificial zone 25 is formed on aluminum-depleted MCrAlY. This depleted areas represent the more erosion resistant in this example Area dar.
  • the MCrAlY layer can also deplete of chromium (Cr), so that the impregnating component 13, for example, has the elements Al and Cr.
  • Both the corrosion products 4 and the sacrificial zone 25 have in the acid bath opposite the material of the layer 22, So the MCrAlY, a higher acid resistance.
  • a rough removal the ceramic thermal barrier coating, the corrosion products or from other areas by mechanical methods e.g.
  • Sandblasting and / or chemical agents, e.g. acid bath respectively.
  • the metal component 13 which in this example is aluminum contains, both in the areas with the corrosion products 4 as well as in the victim zones 25, so that there at least a metal component 13 is present. Only through the enrichment with the metal component 13 may be in an acid bath treatment of the layer system 16 a certain layer thickness Layer 22 (MCrAlY) are removed evenly.
  • MrAlY layer thickness Layer 22
  • the cleaning agent 10 may also include several metallic components 13 (Al, Cr), if that for the composition the corrosion products or the depleted victim zones 25 is required.
  • the metallic component 13 is, for example, with at least one Carrier substance, for example aluminum oxide or aluminum silicate, mixed.
  • the cleaning agent 10 may be metallic Component 13 also in the form of a metal complex.
  • the cleaning agent 10 has at least one activating agent, for example a halogen compound, for example in the form of ammonium chloride (NH 4 Cl).
  • a halogen compound for example in the form of ammonium chloride (NH 4 Cl).
  • the aluminum reacts as metal component 13 with the halogen compound to a gaseous compound.
  • a gaseous compound This is in Example of ammonium chloride aluminum chloride.
  • the gaseous Connection penetrates into the at least one victim zone 25 or makes it possible to diffuse the aluminum into the component 1, by, for example, forming an impregnating layer. Therefore the metal component 13 does not have to be melted. It But it can also be that the gaseous compound only at temperatures above one melting point the at least one impregnating component lies, for example because of a Sublimation occurs.
  • the impregnating component 13 and the activating component are contained in a compound (eg AlF 3 ).
  • the heat treatment forms a gaseous compound aluminum fluoride (AlF).
  • the heat treatment can be carried out in vacuum or inert gases Hydrogen and / or argon are performed.
  • the cleaning agent 10 may, in addition to the metal component 13, the carrier substance and the activating agent one more for example, organic binders (carboxyl methacrylate, carboxyl methyl cellulose, or similar compounds), so that the detergent 10 is a pasty or muddy Has consistency, so the corroded component Apply 1 well and due to the binder on the component 1, 16 can adhere.
  • organic binders carboxyl methacrylate, carboxyl methyl cellulose, or similar compounds
  • the invention is not limited to the said application methods.
  • the concentration is reduced the metal component 13 in the surface 7 facing Range of detergent 10. From this range can only still slightly a metal component 13 or no metal component 13 more diffuse into the component 1. Another one, desired penetration of the metal component 13 in the Depth of the material 1 is found only by further diffusion of Already diffused metal component 13 instead. however would prolong the holding of the component 1 at elevated temperature cause from a surface 11 of the detergent 10, the metal component 13 via the gaseous Connection to surfaces 8 of the component 1 passes on which no detergent 10 was applied and also no penetration the metallic component 13 or the 2Revatis occur is desired.
  • the cleaning agent 10 is removed in this case and another desired penetration of the metal component 13 in the depth of the material 1 takes place by diffusion of already diffused into the component 1 metallic component 13 due to a thermal treatment of the component 1 without Detergent 10 instead.
  • the thermal treatment is bspw. made possible by a solution annealing of the component 1.
  • the removal of the cleaning agent 1 poses no problems because the metallic component 13 is not melted is.
  • the cleaning agent 10 may be local, in particular via the erosion resistant Areas, large or full the component 1, 16 may be applied.
  • the duration of the thermal treatment or the temperature can be based on of calibration curves (diffusion depth depending on time and temperature) of the spatial extent of the corrosion products be adapted in the component.
  • the cleaning agent 10 may before the Heating a mask layer are applied, which prevents that of the surface 11 of the cleaning agent 10 the metallic component 13 reaches surfaces 8 of the component 1, on which no detergent was applied and also no penetration of the metallic component 13 is desired is.
  • the cleaning agent 10 remain on the component 1 and nevertheless a solution annealing is performed to achieve the effect described above.
  • the invention is not limited to parts of gas turbines, but also works for components that have at least one Layer, for example.
  • the invention is not limited to components that have no layers, but their corrosion products removed must be such. in reaction vessels in the chemical industry.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Materials Engineering (AREA)
  • Organic Chemistry (AREA)
  • Metallurgy (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • General Engineering & Computer Science (AREA)
  • General Chemical & Material Sciences (AREA)
  • ing And Chemical Polishing (AREA)
  • Cleaning And De-Greasing Of Metallic Materials By Chemical Methods (AREA)
  • Other Surface Treatments For Metallic Materials (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP01123593A 2001-10-01 2001-10-01 Procédé pour enlever des produits de corrosion d'un composant métallique Withdrawn EP1298230A1 (fr)

Priority Applications (8)

Application Number Priority Date Filing Date Title
EP01123593A EP1298230A1 (fr) 2001-10-01 2001-10-01 Procédé pour enlever des produits de corrosion d'un composant métallique
US10/490,567 US7138065B2 (en) 2001-10-01 2002-05-17 Method for removing at least one area of a layer of a component consisting of metal or a metal compound
JP2003532728A JP2005504179A (ja) 2001-10-01 2002-05-17 金属又は金属化合物から成る部材の少なくとも１つの層範囲の除去方法
PCT/EP2002/005490 WO2003029521A1 (fr) 2001-10-01 2002-05-17 Procede pour enlever au moins une zone de couche d'un composant en metal ou en alliage metallique
DE50202441T DE50202441D1 (de) 2001-10-01 2002-05-17 Verfahren zur entfernung von zumindest einem schichtbereich eines bauteils aus metall oder einer metallverbindung
CNB028170555A CN1328413C (zh) 2001-10-01 2002-05-17 去除由金属或金属化合物构成的一构件的至少一层区的方法
EP02730264A EP1432847B8 (fr) 2001-10-01 2002-05-17 Procede pour enlever au moins une zone de couche d'un composant en metal ou en alliage metallique
US11/541,253 US7429337B2 (en) 2001-10-01 2006-09-29 Method for removing at least one area of a layer of a component consisting of metal or a metal compound

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP01123593A EP1298230A1 (fr) 2001-10-01 2001-10-01 Procédé pour enlever des produits de corrosion d'un composant métallique

Publications (1)

Publication Number Publication Date
EP1298230A1 true EP1298230A1 (fr) 2003-04-02

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Family Applications (2)

Application Number Title Priority Date Filing Date
EP01123593A Withdrawn EP1298230A1 (fr) 2001-10-01 2001-10-01 Procédé pour enlever des produits de corrosion d'un composant métallique
EP02730264A Expired - Lifetime EP1432847B8 (fr) 2001-10-01 2002-05-17 Procede pour enlever au moins une zone de couche d'un composant en metal ou en alliage metallique

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP02730264A Expired - Lifetime EP1432847B8 (fr) 2001-10-01 2002-05-17 Procede pour enlever au moins une zone de couche d'un composant en metal ou en alliage metallique

Country Status (6)

Country Link
US (2) US7138065B2 (fr)
EP (2) EP1298230A1 (fr)
JP (1) JP2005504179A (fr)
CN (1) CN1328413C (fr)
DE (1) DE50202441D1 (fr)
WO (1) WO2003029521A1 (fr)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1870485A1 (fr) * 2006-06-22 2007-12-26 Siemens Aktiengesellschaft Composition et méthode de métallisation d'un composant
EP1870497A1 (fr) * 2006-06-23 2007-12-26 Siemens Aktiengesellschaft Procédé d'enlèvement électrochimique d'un revêtement métallique d'un substrat
WO2009036776A1 (fr) 2007-09-13 2009-03-26 Siemens Aktiengesellschaft Produit sidérurgique résistant à la corrosion pour récipients sous pression, procédé pour sa fabrication, et élément de turbine à gaz
US8673405B2 (en) 2006-08-08 2014-03-18 Siemens Aktiengesellschaft Method for producing a wear layer
WO2015062807A1 (fr) * 2013-10-28 2015-05-07 Aixtron Se Procédé d'élimination de dépôts sur les parois d'une chambre de traitement

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Publication number Priority date Publication date Assignee Title
EP1298230A1 (fr) * 2001-10-01 2003-04-02 Siemens Aktiengesellschaft Procédé pour enlever des produits de corrosion d'un composant métallique
EP1367144A1 (fr) * 2002-05-29 2003-12-03 Siemens Aktiengesellschaft Procédé d'enlèvement des parties d'un composant métallique
EP1676938A1 (fr) * 2004-12-30 2006-07-05 Siemens Aktiengesellschaft Methode de fabrication d'un component d'une turbine et le component d'une turbine
DE102006044416A1 (de) * 2006-09-18 2008-03-27 Siemens Ag Verfahren zum elektrochemischen Be- oder Entschichten von Bauteilen
DE102008004559B4 (de) * 2007-01-23 2017-03-16 General Electric Technology Gmbh Verfahren zum Bearbeiten eines thermisch belasteten Bauteils
CN106757044B (zh) * 2016-12-21 2018-12-14 中国南方航空工业(集团)有限公司 一种空心叶片内腔低熔点合金清理方法
PL429832A1 (pl) * 2019-05-05 2020-11-16 Żrodowski Łukasz Sposób wytwarzania addytywnego trójwymiarowych obiektów
CN115734826A (zh) * 2020-07-03 2023-03-03 应用材料公司 用于翻新航空部件的方法
CN115595581B (zh) * 2022-11-10 2024-04-26 上海电气燃气轮机有限公司 一种服役后热部件粘接层的去除方法

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EP1870485A1 (fr) * 2006-06-22 2007-12-26 Siemens Aktiengesellschaft Composition et méthode de métallisation d'un composant
EP1870497A1 (fr) * 2006-06-23 2007-12-26 Siemens Aktiengesellschaft Procédé d'enlèvement électrochimique d'un revêtement métallique d'un substrat
WO2007147655A1 (fr) * 2006-06-23 2007-12-27 Siemens Aktiengesellschaft Procédé pour éliminer par voie électrochimique un revêtement situé sur un élément
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WO2015062807A1 (fr) * 2013-10-28 2015-05-07 Aixtron Se Procédé d'élimination de dépôts sur les parois d'une chambre de traitement

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US7429337B2 (en) 2008-09-30
EP1432847B1 (fr) 2005-03-09
US20070023392A1 (en) 2007-02-01
WO2003029521A1 (fr) 2003-04-10
EP1432847B8 (fr) 2005-06-29
US7138065B2 (en) 2006-11-21
CN1549874A (zh) 2004-11-24
JP2005504179A (ja) 2005-02-10
DE50202441D1 (de) 2005-04-14
EP1432847A1 (fr) 2004-06-30
US20040244817A1 (en) 2004-12-09
CN1328413C (zh) 2007-07-25

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